Fluid flow control apparatus

ABSTRACT

A fluidic diversion valve, having improved net thrust efficiency, comprises a shunt-staged vortex valve device in which vortex amplifier valves in each of a pair of branches are staged in series with an ejector-diffuser element, and at least a pair of corresponding ones of the amplifier valves have their control ports connected to one another through a cross-bleed conduit.

United States Patent 151 3,692,036 Kaufman 1 Sept. 19, 1972 [54] FLUIDFLOW CONTROL APPARATUS 3,490,474 l/ 1970 Larson ..137/81.5 3,587 6056/1971 Verplank ..137/81.5 F. K t S t A [72] Inventor 25:? a man an a na3,493,003 2/1970 Peoples ..l37/81.5 3,521,653 7/1970 Becker et a1..137/81.5 1 Assignw Philco-Ford Corporation, Phlladel- 3,598,137 8/1971Glaze ..137/s1.5 Phla, 3,636,964 l/l972 Colamussi et al.....137/81.5 X22 F'] d: A 118 1971 1 1e pr Primary Examiner-Samuel Scott PP N05132,314 Attorney-Robert D. Sanborn 52 us. c1 ..137/s1.s 1571 ABSTRACT[51] Ill. Cl. ..Fl5c 1/16 A fluidic diversion Valve having improved netthrust [58] Field of Search ..137/81.5 efficiency, comprises ashunbstaged vortex valve device in which vortex amplifier valves in eachof a [56] References cited pair of branches are staged in series with anejector- UNITED STATES PATENTS diffuser element, and at least a pair ofcorresponding ones of the amplifier valves have their control ports 31 16/ 1969 Camarata "137N315 X connected to one another through across-bleed con- 3,456,667 7/1969 Mayer ..137/8l.5 duiL 3,473,54510/1969 Boyadjieff ..137/81.5 3,486,521 12/1969 Mayer ..137/81.5 7Claims, 4 Drawing Figures MAI/V fill/0 fol/RC! /8 tl 3 /0 E I! /6 I6 I 120 PATENTEDSEP 19 I972 3.692.036

a agllyw BY I BACKGROUND OF THE INVENTION This invention relates tofluid flow control apparatus, and especially to improvements in fluidicdiversion valves.

While of broader applicability, apparatus embodying the invention hasespecial utilityin the reaction control of flight vehicles that areoperational over a range of environmental pressure levels as areencountered between sea level and outer space.

It is a general objective of this invention to provide fluidic diversionvalve means of the above described general type having operationalcharacteristics that are independent of an external pressureenvironment.

It is a further and more specific objective of the invention to provideimproved diversion valvemeans for controlling the flow of hightemperature gaseous fluid, which valve will operate rapidly with minimalstress on functional components.

SUMMARY OF THE INVENTION To the foregoing general ends, the inventioncontemplates fluidic diversion valve apparatus comprising an inletnozzle, and a pair of identical outlet duct means each fed by said inletnozzle and terminating in an outlet thrust nozzle. lnterposed in each ofthe ducts, in series flow circuit between the inlet and outlet nozzles,are a first vortex fluid amplifier, an ejector-diffuser, and a secondvortex valve fluid amplifier. Each ejectordiffuser comprises asupersonic primary nozzle, a highvelocity, low-pressure free jet region,and a supersonic diffuser. The free jet region is in fluid flowcommunication with the like region of the other duct, and, in one aspectof the invention, the control port of one of the second vortex fluidamplifiers is in fluid flow communication with the like control port inthe other duct.

Advantageously, the disclosed fluidic diversion valve apparatus achievesimproved net thrust efficiency over a range of surrounding pressuresthrough its capability for minimizing leakage through the off" thrustnozzle substantially independently of the surrounding pressure.

For a further understanding of the invention, and the manner in whichits objectives and advantages may best be achieved, reference is made tothe following description, taken in light of theaccompanying drawmg.

BRIEF DESCRIPTION OF THE DRAWING FIG. 1 is an elevational showing,partly in section and with parts broken away, illustrating diversionvalve apparatus embodying the invention, and further including showingof a preferred known form of auxiliary control means for portions of theapparatus;

FIG. 2 is a sectional showing of a portion of the apparatus seen in FIG.1, taken generally along the line indicated by arrows 2-2 applied toFIG. 1;

FIG. 3 is a sectional showing of a portion of the apparatus seen in FIG.1, taken generally along the line indicated by arrows 3-3 applied toFIG. 1; and

FIG. 4 is a somewhat diagrammatic showing of a portion of the apparatusillustrated in FIG. 1, demonstrating operational features thereof.

DESCRIPTION OF THE PREFERRED EMBODIMENT With more detailed reference toFIGS. 1, 2 and 3, a

fluidic diversion valve 10 comprises a primary nozzle 11 disposed influid flow communication with a pair of duct means 12 and 13 identicalwith one another. In view of the identity of duct means 12 and 13, likenumerals will be used to designate like parts thereof. Each of ductmeans 12 and 13 includes, in series fluid flow circuit, a first stagepilot valve 18, a second stage vortex fluid amplifier 14, a third stageejector-diffuser section 15, a fourth stage vortex fluid amplifier l6,and a reaction nozzle 17.

The first stage pilot valve 18 is of the electromechanically actuatedflapper, flow proportioning type, and receives its fluid supply throughport 19 communicating with the Main Fluid Source in a region immediatelyupstream of nozzle 11. The outlet conduits of flow proportioning pilotvalve 18 are arranged to supply selectively proportioned quantities ofcontrol fluid to the vortex-inducing control ports 20 of the secondstage vortex fluid amplifiers 14. A valve suitable for use as pilotvalve 18, for purposes of the present invention, is disclosed andclaimed in U.S. Pat. No. 3,215,162, assigned to the Ford Motor Company.It will of course be understood that other suitable means may be used tosupply fluid to control ports 20.

Each of the vortex fluid amplifiers 14 comprises an annular inlet portdefined by the annular space i 25 (FIG. 2) between the confrontingcurved side wall of a generally diskshaped member 26 and the generallycylindrical walls 27 of a vortex chamber. A vortex-inducing control port20 ispositioned in tangential relationship to thevortex chamber in theregion of the diskshaped member.

Each of the third stage, ejector diffuser sections 15 includes asupersonic primary nozzle 31, a highvelocity, low-pressure free jetregion 32, and a supersonic fluid diffuser 33. Fluid entering theprimary nozzle 31 from vortex fluid amplifier 14 at near-stagnationconditions is accelerated to supersonic velocity as it traverses thefree jet region 32 to enter the supersonic diffuser 33. The staticpressureof the free jet region 32 is sufiiciently low to effectentrainment of fluid at the bleed ports 32. Both primary fluid andentrained fluid are decelerated in the supersonic diffuser 33 to affordhigh working pressures in the next, or fourth, stage 16. The bleed ports23 of the ejector-diffuser sections 15 are connected to one another byan annular cross-bleed conduit 24, for purposes more fully to beexplained in connection with a description of the operation of theapparatus.

Each of the vortex fluid amplifiers 16 comprises an annular inlet portdefined by the annular space 28 (FIG. 3) between the confronting curvedside wall of a disk-shaped member 29 and the curved wall 30 of a vortexchamber. A vortex-inducing, control port 21 is provided in the chamberwall 30, in the region of diskshaped member 29. Gas fluid flowing from avortex fluid amplifier 16 is discharged through a corresponding reactionnozzle 17, and control ports 21 of the fourth stage vortex fluidamplifiers 116 are connected to one another through a cross-bleedconduit 22.

In operation of the apparatus, and with reference to FIG. 4, let it beassumed that gaseous fluid is flowing through primary nozzle 11, andthat it is desired to effect substantially full discharge gas flow fromleft-hand reaction nozzle 17, to the exclusion of any significant flowthrough right-hand reaction nozzle 17. The aforementioned discharge flowis achieved by energizing pilot valve 18 (FIG. 1) so as to directcontrol flow into right-hand flow control port 20, thereby to effectvortex gas flow within right-hand chamber 14 and through right-handnozzle 31. Creation of this vortex effectively blocks full flow of gasthrough right-hand nozzle 31, so that substantially all gas issuing fromnozzle 11 is caused to flow through left-hand vortex fluid amplifier l4,and exit therefrom through left-hand nozzle 31 at supersonic velocity.The free jet region 32 flows at low static pressure, and induces leakagegas issuing from right-hand nozzle 31 to flow (broken line arrows)through cross-bleed conduit 24 (broken line arrows) and become entrainedin the left-hand free jet region 32, for flow into left-hand supersonicdiffuser 33 (solid line arrows), where static pressure is recovered. Themain gas stream then flows outwardly from diffuser 33, through annularpassage 28 of left-hand vortex amplifier 16, and outwardly throughleft-hand reaction nozzle 17 in performance of a desired controlfunction. 7

Further to reduce leakage gas flow through righthand reaction nozzle 17,a portion of the gas flowing through left-hand vortex amplifier 16 isbled through left-hand control port 21, flows through conduit 22 (brokenline arrows) and through right-hand control port 21, where it creates agas flow-blocking vortex (broken line arrows) in the chamber ofright-hand vortex amplifier 16. This vortex-inducing gas, together withany leakage gas, bleeds substantially ineffectively outwardly ofright-hand reaction nozzle 17, as is further indicated by broken lineflow arrows. Gas flow blockage through a duct 12 or 13 is effective atsealevel as well as at higher altitudes, since the disclosed successivestaging of vortex valves 14 and 16, in series gas flow circuit withejector-diffusers 15 achieves positive control of gas flow independentlyof surrounding back pressure.

To divert reactive gas flow for discharge from righthand nozzle'l7,pilot valve 18 is operated to direct control flow through left-handcontrol port 20, whereupon the main and control gas flow pathssubstantially instantaneously are reversed, to become essentially amirror image of the paths illustrated in FIG. 4.

It will therefore be appreciated that the invention affords attainmentof optimum reactive net thrust efficiency, characterized by minimumleakage through the off" side thrust nozzle over a wide range ofenvironmental pressure conditions.

1 claim:

1. Fluid flow control apparatus comprising, in combination a primaryfluid flow nozzle and a pair of identical fluid flow duct means fed bysaid nozzle; each said duct means including a first vortex fluidamplifier, a supersonic primary nozzle having its inlet in fluid flowcommunication with the outlet of said first vortex fluid amplifier, asupersonic diffuser spaced from and having its inlet fed by the outletof said supersonic primary nozzle thereby defining a free jet regiontherebetween, a second vortex fluid amplifier fed by said supersonicdiffuser, and a reaction noule having its inlet in fluid flowcommunication with the outlet of said second vortex fluid amplifier;passage means providing fluid flow communication between each of therecited free jet regions of said pair of duct means; means forcontrolling the flow of fluid to and from the control ports of each ofsaid second vortex fluid amplifiers; and means for modulating controlfluid flow through the control ports of each of said first vortex fluidamplifiers in establishment of major fluid flow, selectively, throughone or the other of said pair of duct means for discharge by acorresponding reaction nozzle.

2. Apparatus according to claim 1 and further characterized in that saidmeans for controlling the flow of fluid to and from said control portsof said second vortex fluid amplifiers comprises a cross-bleed ductinterconnecting said last recited control ports.

3. Apparatus according to claim 1 and further characterized in that saidlast recited means for modulating control fluid flow comprises a pilotvalve having an inlet port arranged to withdraw fluid from the mainfluid stream passing through said primary nozzle, a pair of oppositelydisposed outlet ports each arranged to feed fluid to one of said controlports of said first vortex fluid amplifiers, and means for controllingthe relative rates of fluid flow through said outlet ports.

4. Apparatus according to claim 3, and further characterized in thatsaid means for controlling the flow of fluid to and from said controlports of said pair of second vortex fluid amplifiers comprises conduitmeans establishing fluid flow communication between said last recitedcontrol ports.

5. A fluidic diversion valve apparatus especially adapted for use as areaction thruster in the attitude control of a flight vehicle or thelike and having improved net thrust efficiency over a relatively widerange of altitudes, said apparatus comprising: a primary fluid flownozzle adapted for connection to a source of pressurized fluid, and apair of identical fluid flow duct means fed by said primary nozzle, eachsaid duct means including, in series fluid flow circuit, a first vortexfluid amplifier, a supersonic primary nozzle having its inlet in fluidflow communication with the outlet port of said first vortex fluidamplifier, a supersonic diffuser spaced from and having its inlet fed bythe outlet of said supersonic primary nozzle whereby to define a freejet region therebetween, a second vortex fluid amplifier fed by saidsupersonic diffuser, and a reaction thrust nozzle having its inlet influid flow communication with the outlet port of said second vortexfluid amplifier; conduit means providing fluid flow communicationbetween each of the recited free jet regions of said pair of duct means;means for controlling the flow of fluid to and from the control ports ofeach of said second vortex fluid amplifiers; and means providing forflow of control fluid selectively through one or the other of thecontrol ports of each of said first vortex fluid amplifiers inestablishment of major fluid flow through one or the other of said pairof duct means for outflow from a corresponding reaction thrust nozzle inachievement of the recited attitude control.

6. Apparatus according to claim 5, and further characterized in that theinlet port of each of said vortex fluid amplifier is of annularconfiguration.

7. Apparatus according to claim 5, and further characterized in thatsaid means for controlling-the flow of fluid to and from said controlports of said pair of second vortex fluid amplifiers comprises conduitmeans establishing fluid flow communication between 5 said last recitedcontrol ports.

1. Fluid flow control apparatus comprising, in combination a primaryfluid flow nozzle and a pair of identical fluid flow duct means fed bysaid nozzle; each said duct means including a first vortex fluidamplifier, a supersonic primary nozzle having its inlet in fluid flowcommunication with the outlet of said first vortex fluid amplifier, asupersonic diffuser spaced from and having its inlet fed by the outletof said supersonic primary nozzle thereby defining a free jet regiontherebetween, a second vortex fluid amplifier fed by said supersonicdiffuser, and a reaction nozzle having its inlet in fluid flowcommunication with the outlet of said second vortex fluid amplifier;passage means providing fluid flow communication between each of therecited free jet regions of said pair of duct means; means forcontrolling the flow of fluid to and from the control ports of each ofsaid second vortex fluid amplifiers; and means for modulating controlfluid flow through the control ports of each of said first vortex fluidamplifiers in establishment of major fluid flow, selectively, throughone or the other of said pair of duct means for discharge by acorresponding reaction nozzle.
 2. Apparatus according to claim 1 andfurther characterized in that said means for controlling the flow offluid to and from said control ports of said second vortex fluidamplifiers comprises a cross-bleed duct interconnecting said lastrecited control ports.
 3. Apparatus according to claim 1 and furthercharacterized in that said last recited means for modulating controlfluid flow comprises a pilot valve having an inlet port arranged towithdraw fluid from the main fluid stream passing through said Primarynozzle, a pair of oppositely disposed outlet ports each arranged to feedfluid to one of said control ports of said first vortex fluidamplifiers, and means for controlling the relative rates of fluid flowthrough said outlet ports.
 4. Apparatus according to claim 3, andfurther characterized in that said means for controlling the flow offluid to and from said control ports of said pair of second vortex fluidamplifiers comprises conduit means establishing fluid flow communicationbetween said last recited control ports.
 5. A fluidic diversion valveapparatus especially adapted for use as a reaction thruster in theattitude control of a flight vehicle or the like and having improved netthrust efficiency over a relatively wide range of altitudes, saidapparatus comprising: a primary fluid flow nozzle adapted for connectionto a source of pressurized fluid, and a pair of identical fluid flowduct means fed by said primary nozzle, each said duct means including,in series fluid flow circuit, a first vortex fluid amplifier, asupersonic primary nozzle having its inlet in fluid flow communicationwith the outlet port of said first vortex fluid amplifier, a supersonicdiffuser spaced from and having its inlet fed by the outlet of saidsupersonic primary nozzle whereby to define a free jet regiontherebetween, a second vortex fluid amplifier fed by said supersonicdiffuser, and a reaction thrust nozzle having its inlet in fluid flowcommunication with the outlet port of said second vortex fluidamplifier; conduit means providing fluid flow communication between eachof the recited free jet regions of said pair of duct means; means forcontrolling the flow of fluid to and from the control ports of each ofsaid second vortex fluid amplifiers; and means providing for flow ofcontrol fluid selectively through one or the other of the control portsof each of said first vortex fluid amplifiers in establishment of majorfluid flow through one or the other of said pair of duct means foroutflow from a corresponding reaction thrust nozzle in achievement ofthe recited attitude control.
 6. Apparatus according to claim 5, andfurther characterized in that the inlet port of each of said vortexfluid amplifier is of annular configuration.
 7. Apparatus according toclaim 5, and further characterized in that said means for controllingthe flow of fluid to and from said control ports of said pair of secondvortex fluid amplifiers comprises conduit means establishing fluid flowcommunication between said last recited control ports.